Relevant bibliographies by topics / Landing gear cooling system

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Landing gear cooling system'

Author: Grafiati
Published: 30 May 2022
Last updated: 31 July 2025

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Journal articles on the topic "Landing gear cooling system"

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Jan, Wajid, Muhammad Farooq, Jamel Baili, Rehan Ali Shah, Aamir Khan, and Hijaz Ahmad. "Magnetic field dependent viscous fluid-flow between squeezing plates with homogeneous and heterogeneous reactions." Thermal Science 25, Spec. issue 2 (2021): 423–31. http://dx.doi.org/10.2298/tsci21s2423j.

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The impacts of magnetic field dependent viscous fluid is explored between squeezing plates in the presence of homogeneous and heterogeneous reactions. The unsteady constitutive equations of heat and mass transfers, modified Navier-Stokes, magnetic field and homogeneous and heterogeneous reactions are coupled as an system of ODE. The appropriate solutions are established for the vertical and axial induced magnetic field equations for the transformed and momentum as well as for the MHD pressure and torque exerted on the upper plate, and are in details. In the case of a smooth plate, the self-sim
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Dai, Xin, Lu Liu, Qing Xu, Fangfang Xu, and Xiaotian Hu. "Research on the control technology of aircraft landing gear buffer variable stroke." Journal of Physics: Conference Series 2820, no. 1 (2024): 012010. http://dx.doi.org/10.1088/1742-6596/2820/1/012010.

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Abstract The landing gear performance test is an essential part of the aircraft development process. In order to simulate the state of the landing gear during take-off, cruise, and landing, the landing gear buffer is required to have the function of self-variable stroke. This paper proposes a new method to establish a variable travel control system for the landing gear buffer, which realizes the automatic adjustment of the buffer so that the landing gear fatigue test can be implemented quickly and accurately. In the test verification, with the help of the aircraft landing gear fatigue test jig
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Guo, Wei Gang, and Wei Han. "Modeling and Faults Simulation of Aircraft Landing Gear System." Applied Mechanics and Materials 333-335 (July 2013): 2021–24. http://dx.doi.org/10.4028/www.scientific.net/amm.333-335.2021.

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The model of aircraft landing gear hydraulic system is build by software of AMESim. Under the AMESim environment, a hydraulic simulation of the nose landing gear of aircraft is constructed. The simulation model of the component is built by graphical modeling method. Setting two case faults parameters of landing gear actuating cylinder leakage and air into oil, it obtains faults symptom of hydraulic system. The Internal characteristics, Interrelation and motion Law is shown for landing gear system various components. Combining hydraulic system simulation with fault diagnosis effectively, it can
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Shukla, Dr Anoopkumar. "Design and Analysis of Drone Landing Gear for Agriculture." International Scientific Journal of Engineering and Management 03, no. 04 (2024): 1–9. http://dx.doi.org/10.55041/isjem01527.

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This study aim to design and analysis of drone landing gear with spring suspension for agriculture. A literature review was conducted to examine the existing research on the topic of agricultural drone and it’s landing gear. Then testing present landing gear has been done and also the designing and analysis of new landing gear with suspension has been done. The result show that the drones landing gear without suspension break easily. This also shows that the landing gear with suspension have more life time then the landing gear without suspensions system. Key Words:agricultural, drone, spring
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Parat, Camille, Zu-Yun Li, and Jing-Shan Zhao. "Design and stiffness analysis of an overconstrained landing gear retraction mechanism with four side-stays." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 12 (2019): 4421–35. http://dx.doi.org/10.1177/0954410018824509.

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It is the first mission for a landing gear retraction system to extend the structure during the phases of take-off and landing of the flight. Besides, the structure should be available to improve the reliability, strength and stability of the system while reducing the influence of the landing gear on the total drag. However, a large number of airplane accidents are due to the malfunctions or failures of the landing gear retraction system. In this paper, a novel design of retraction system is proposed. Instead of having only one side-stay to execute the desired motion, this new design proposed
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Liang, Yong, Kun Zhao, Yingchun Chen, Longjun Zhang, and Gareth J. Bennett. "An Experimental Characterization on the Acoustic Performance of Forward/Rearward Retraction of a Nose Landing Gear." International Journal of Aerospace Engineering 2019 (July 4, 2019): 1–11. http://dx.doi.org/10.1155/2019/4135094.

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The modern undercarriage system of a large aircraft normally requires the landing gear to be retractable. The nose landing gear, installed in the front of the fuselage, is retracted either forward or rearward. In the forward/rearward retraction system, the landing gear is normally installed to the trailing/leading side of the bay. When the incoming flow passes the landing gear as well as the bay, the installation that corresponds to the forward/rearward retraction system has a significant impact on the coupling flow and the associated noise of the landing gear and the bay. In this paper, acous
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Wang, Jian Feng, Xian Yu Zhang, and Hong Wei Wang. "The Semi-Active Optimal Control Method of Aircraft Landing Gear." Applied Mechanics and Materials 159 (March 2012): 390–94. http://dx.doi.org/10.4028/www.scientific.net/amm.159.390.

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When designing a landing gear damper, it is well-known that damper characteristics required for good handling are not the same as those required for good ride comfort. Semi-active control landing gear damper, as their name implies, fill the gap between purely passive damper and fully active control Langing gear-control systems and offer the reliability of passive systems, yet maintain the versatility and adaptability of fully active devices. During recent years there has been considerable interest towards theoretical study and practical practical implementation of this semi-active control land
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NICOLIN, Ilie, and Bogdan Adrian NICOLIN. "Research on the nose landing gear of a military training aircraft." INCAS BULLETIN 12, no. 4 (2020): 249–59. http://dx.doi.org/10.13111/2066-8201.2020.12.4.23.

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This paper presents the analysis of the landing gear configurations and the proposal of a solution for a military training aircraft. The paper presents both landing gears: nose and main because they are inextricably linked. The nose landing gear of military aircraft is a complex system composed of structural elements, electric and hydraulic components, energy absorption components, aircraft tire wheels etc., which is dimensioned according to the weight of the aircraft. Additional components attached to the nose landing gear include a landing gear extension and retraction mechanism and a steeri
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Zhang, Ming, Dafu Xu, Shuai Yue, and Haifeng Tao. "Design and dynamic analysis of landing gear system in vertical takeoff and vertical landing reusable launch vehicle." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 10 (2018): 3700–3713. http://dx.doi.org/10.1177/0954410018804093.

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Landing gear system is a key part of the implementation of reusable vertical takeoff and vertical landing launch vehicle, where its buffing performance is directly related to the vehicle whether it can land safely or stably. According to the reusable launch vehicle general scheme, outrigger landing legs are designed, and the hydraulic absorber is used for the landing gear system. Meanwhile, a scaling principle prototype of landing gear system is developed, and the landing impact test is carried out. A dynamic simulation model of the landing vehicle has been set up, researching the influence of
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Tartaglia, Carmine Carandente, Maurizio Arena, Giovanni Bruno, et al. "Vibration Test campaign performed on a Landing Gear System." Journal of Physics: Conference Series 2716, no. 1 (2024): 012026. http://dx.doi.org/10.1088/1742-6596/2716/1/012026.

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Abstract The landing gear system is one of the most critical systems of the aircraft. The need to design a landing gear with high performance, longer life and with a significant reduction in terms of weight, production and maintenance costs represents a real challenge for a sustainable future that Europe is heralding. This paper presents the results of the experimental campaign of vibration tests performed on the main and side landing gear system, in both extended and retracted configurations, to be installed on the AIRBUS Group/Helicopter RACER compound helicopter demonstrator and it is part
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Dissertations / Theses on the topic "Landing gear cooling system"

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Lin, Tianhong, and Тяньхун Лінь. "Preliminary design of long range cargo aircraft with 240 passengers." Thesis, National Aviation University, 2021. https://er.nau.edu.ua/handle/NAU/53188.

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Робота публікується згідно наказу Ректора НАУ від 27.05.2021 р. №311/од "Про розміщення кваліфікаційних робіт здобувачів вищої освіти в репозиторії університету". Керівник роботи: доцент, к.т.н. Юцкевич Святослав Сергійович<br>This diploma work is dedicated to the design of cargo long-range aircraft with passenger capacity 240 and its design characteristic estimation. The methods of design are analysis of the prototypes and selections of the most advanced technical decisions, analysis of center of gravity position. The diploma work contains drawings of the long-range aircraft with a carrying
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Heckman, Nancy L. Kolar Ramesh. "Testing a wheeled landing gear system for the TH-57 helicopter." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from the National Technical Information Service, 1992. http://handle.dtic.mil/100.2/ADA262152.

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Heckman, Nancy L. "Testing a wheeled landing gear system for the TH-57 helicopter." Thesis, Monterey, California. Naval Postgraduate School, 1992. http://hdl.handle.net/10945/24068.

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Using the main gear from a Cessna 182 and the nose gear from a Grumman AAI-B, (patent pending) a comparison with the skid gear currently installed on the TH-57 helicopters was conducted. The initial comparison was done using a structural analysis program, GIFTS, to simultaneously analyze and compare the gear systems. Experimental data was used to verify program results. Experimental testing was conducted for further code validation and analysis of each system's advantages and disadvantages. While the benefits of a wheeled system merit further study, the system analyzed requires modification to
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Sulcs, Peter, Carl Palmer, John Naber, Doug Jackson, Lynn Fuller, and Charles H. Jones. "Wireless Tire Temperature Sensor Patch and System for Aircraft Landing Gear Testing." International Foundation for Telemetering, 2010. http://hdl.handle.net/10150/604251.

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ITC/USA 2010 Conference Proceedings / The Forty-Sixth Annual International Telemetering Conference and Technical Exhibition / October 25-28, 2010 / Town and Country Resort & Convention Center, San Diego, California<br>Testing aircraft brake and tire systems often results in tire temperatures that makes the aircraft unsafe to approach (due to explosion risk) for up to 45 minutes; this complicates cost effective test execution. This paper describes work on a wireless sensor system that measures multiple tire temperatures and transmits the data to someone at a safe distance (>300 ft). The solutio
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Yang, Yang. "Aircraft landing gear extension and retraction control system diagnostics, prognostics and health management." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7266.

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This thesis contains the Group Design Project (GDP) work and Individual Research Project (IRP) work. The target of this GDP was to design a long range flying wing passenger aircraft to meet the increasing global aircraft demand. The name of this flying wing aircraft is FW-11. This is a project cooperated between Aviation Industry Corporation of China (AVIC) and Cranfield University. The writer was involved in the conceptual design stage of this project. The author was in charge of the engine market, engine selection, engine sizing and performance. The target of the IRP is to build a set of hea
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Gallimore, Craig Allen. "Passive Viscoelastic Constrained Layer Damping Application for a Small Aircraft Landing Gear System." Thesis, Virginia Tech, 2008. http://hdl.handle.net/10919/35350.

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The main purpose of this report was to test several common viscoelastic polymers and identify key attributes of their applicability to a small aircraft landing gear system for improved damping performance. The applied viscoelastic damping treatment to the gear was of a constrained layer type, promoting increased shear deformation over free surface treatments, and therefore enhanced energy dissipation within the viscoelastic layer. A total of eight materials were tested and analyzed using cyclic loading equipment to establish approximate storage modulus and loss factor data at varying loading
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Terkovics, Nándor. "A feasibility study on applying real-time dynamic substructuring to a nonlinear landing gear fuselage system." Thesis, University of Bristol, 2014. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.683561.

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Aircraft nose landing gear must be tested for shimmy oscillations experimentally. Current test methods consider the landing gear as stand alone systems without the possibility of accounting for the dynamics of the fuselage which they are attached to. This means that all possible interaction between them is ignored during the experiment which, if the interaction for specific conditions is significant, might reduce the reliability of the test results. On the other hand, conducting a full scale experiment on the aircraft would be impractical due to size and related costs. In this thesis the nonli
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Skřivánek, Jan. "Návrh elektro-hydraulického ovládání hlavního podvozku a brzd pro malý cvičný letoun." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2018. http://www.nusl.cz/ntk/nusl-377525.

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This thesis studies the design of an electro-hydraulic landing gear and brakes control system of a trainer aeroplane. In the first part there is a basic draft of the landing gear kinematics and its loads during gear retraction, flight and landing. Braking conditions are also analysed. The thesis then focuses on the design of hydraulic circuits and their control. Simulations for studying the dynamic characteristics of the braking proportional valve and the course of plane braking were created in Simulink. There is also a brief section about reliability of the proposed system.
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Vodička, Petr. "Návrh elektro-hydraulické soustavy pro ovládání příďového podvozku malého dopravního letounu." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2017. http://www.nusl.cz/ntk/nusl-318402.

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The diploma thesis is focused on design of electrohydraulic system for nose gear control on small civil airliners. First part consists of brief review of small civil airliners, nose gears and CS 23 restrictions relevant for the design. In practical part a typical small civil airliner is defined and kinematic of landing gear mechanisms is designed. Then the electrohydraulic system itself is designed and parameters of some components are suggested. The wheel steering mechanism is simulated and, in conclusion, the whole system is evaluated.
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Javůrek, František. "Regálový zakladač pro ukládání palet v automatickém skladu." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2010. http://www.nusl.cz/ntk/nusl-229163.

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Target of the submitted work was a proposal of a new type of shelf stackers in the range from 8 to 36 m that are working in fully automated warehouses. By using a fully automated storage system all human supervision in ordering pallets in a warehouse are canceled and everything is taken over by the control system. These stores are very efficient and save both time and money. With regard to safety requirements, regular inspections should be provided to the system. At the beginning of this work, there was done a short introduction to the particular study including the description of basic parts
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Books on the topic "Landing gear cooling system"

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Walker, Richard William Reid. Implementation of an aircraft shock strut and steering system model in real time. Dept. of Aerospace Science and Engineering, 1986.

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Heckman, Nancy L. Testing a wheeled landing gear system for the TH-57 helicopter. Naval Postgraduate School, 1992.

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3

H, Daugherty Robert, Martinson Veloria J, and Langley Research Center, eds. Modeling and validation of a Navy A6-Intruder actively controlled landing gear system. National Aeronautics and Space Administration, Langley Research Center, 1999.

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H, Daugherty Robert, Martinson Veloria J, and Langley Research Center, eds. Modeling and validation of a Navy A6-Intruder actively controlled landing gear system. National Aeronautics and Space Administration, Langley Research Center, 1999.

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Landing gear system development plan. Society of Automotive Engineers, 1985.

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Schmidt, Robert Kyle. The Design of Aircraft Landing Gear. SAE International, 2021. http://dx.doi.org/10.4271/9780768099430.

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The aircraft landing gear and its associated systems represent a compelling design challenge: simultaneously a system, a structure, and a machine, it supports the aircraft on the ground, absorbs landing and braking energy, permits maneuvering, and retracts to minimize aircraft drag. Yet, as it is not required during flight, it also represents dead weight and significant effort must be made to minimize its total mass. The Design of Aircraft Landing Gear, written by R. Kyle Schmidt, PE (B.A.Sc. - Mechanical Engineering, M.Sc. - Safety and Aircraft Accident Investigation, Chairman of the SAE A-5
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Testing a Wheeled Landing Gear System for the Th-57 Helicopter (Ada262152/Ll). Natl Technical Information, 1992.

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National Aeronautics and Space Administration (NASA) Staff. Modeling and Validation of a Navy A6-Intruder Actively Controlled Landing Gear System. Independently Published, 2018.

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Book chapters on the topic "Landing gear cooling system"

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Boniol, Frédéric, and Virginie Wiels. "The Landing Gear System Case Study." In Communications in Computer and Information Science. Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-07512-9_1.

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Zheng, Bosi, and Huiting Yin. "QFD Based Conceptual Design of Civil Aircraft Landing Gear." In Lecture Notes in Mechanical Engineering. Springer Nature Singapore, 2025. https://doi.org/10.1007/978-981-97-7887-4_43.

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Abstract Landing gear system plays an important role in the process of takeoff and landing, and it’s a critical part to ensure flight operation safety, thus the landing gear design occupies a crucial position in aircraft design process. The conceptual design of landing gear is the first step of whole design process, which largely determines the final design results. The application of QFD (Quality Function Deployment) method in landing gear system can build a conversion model from landing gear system requirements to technical characteristics, parts and manufacturing process. While the applicat
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Dhaussy, Philippe, and Ciprian Teodorov. "Context-Aware Verification of a Landing Gear System." In Communications in Computer and Information Science. Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-07512-9_4.

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Mammar, Amel, and Régine Laleau. "Modeling a Landing Gear System in Event-B." In Communications in Computer and Information Science. Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-07512-9_6.

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Tartaruga, I., J. E. Cooper, M. H. Lowenberg, P. Sartor, and Y. Lemmens. "Optimization of a Landing Gear System Including Uncertainties." In 14th International Probabilistic Workshop. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-47886-9_30.

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Du, Xiaolei, and Yong Xu. "Dynamical Behaviours of the Nose Landing Gear with Freeplay and Stochastic Disturbance." In Lecture Notes in Mechanical Engineering. Springer Nature Switzerland, 2024. http://dx.doi.org/10.1007/978-3-031-70392-8_68.

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AbstractShimmy dynamics of a dual wheel nose landing gear system with torsional freeplay under stochastic lateral disturbances is studied. Dynamic characteristics of the deterministic case are numerically analyzed, especially the shimmy of the landing gear through bifurcation analysis. Meanwhile, the influences of the freeplay nonlinearity on shimmy behaviours are examined in detail. Impacts of stochastic lateral disturbances on the shimmy of the landing gear system are performed via time history and recurrence plots. Our results show that the interaction between the freeplay nonlinearity and
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Hansen, Dominik, Lukas Ladenberger, Harald Wiegard, Jens Bendisposto, and Michael Leuschel. "Validation of the ABZ Landing Gear System Using ProB." In Communications in Computer and Information Science. Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-07512-9_5.

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Cristiá, Maximiliano, and Gianfranco Rossi. "An Automatically Verified Prototype of a Landing Gear System." In Lecture Notes in Computer Science. Springer Nature Switzerland, 2024. http://dx.doi.org/10.1007/978-3-031-55248-9_3.

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Arcaini, Paolo, Angelo Gargantini, and Elvinia Riccobene. "Modeling and Analyzing Using ASMs: The Landing Gear System Case Study." In Communications in Computer and Information Science. Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-07512-9_3.

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Khanapuri, Eshaan M., and Mahesh Rao. "Concept of Automatic Landing Gear System with Altitude and Distance as Parameters." In Proceedings of International Conference on Cognition and Recognition. Springer Singapore, 2017. http://dx.doi.org/10.1007/978-981-10-5146-3_7.

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Conference papers on the topic "Landing gear cooling system"

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Zhou, Lingchen, Pianpian Zuo, Kai Li, Hongyu Zhu, Shupei He, and Meihui Su. "Landing Gear Alert Design of Civil Aircraft Based on System Engineering." In 2024 10th Asia Conference on Mechanical Engineering and Aerospace Engineering (MEAE). IEEE, 2024. https://doi.org/10.1109/meae62008.2024.11026451.

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Zhang, Jun, Xu Jiang, Yizhuang Ding, and Aiguo Song. "A Cable-Driven and Rigid-Flexible Structures Coupled Landing Gear System for Spacecraft Soft Landing on Asteroids." In 2024 IEEE/ASME International Conference on Advanced Intelligent Mechatronics (AIM). IEEE, 2024. http://dx.doi.org/10.1109/aim55361.2024.10637151.

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Jiang, Chengjie, and Xiaolan Cheng. "Research on Seal Performance of Civil Aircraft Landing Gear Shock Absorbing System." In 2024 10th Asia Conference on Mechanical Engineering and Aerospace Engineering (MEAE). IEEE, 2024. https://doi.org/10.1109/meae62008.2024.11026067.

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Langley, Jared, and Mark Costello. "Ground Resonance Mitigation of Rotorcraft with Articulated Robotic Landing Gear: A Preliminary Investigation." In Vertical Flight Society 72nd Annual Forum & Technology Display. The Vertical Flight Society, 2016. http://dx.doi.org/10.4050/f-0072-2016-11443.

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Ground resonance is a serious aeromechanical instability in helicopters that results from hub motion coupling with lag motion of the rotor blades when the vehicle is in contact with a surface. Nearly all recent methods to mitigate ground resonance instability rely on a passive or semi-active lag damper. These lag dampers, however, are generally undesirable for rotorcraft design and maintenance. Current innovations in rotorcraft landing gear have created an alternative approach to ground resonance mitigation. Recent work has demonstrated the capabilities of an articulated landing gear system as
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Zhang, Lei, Xinlong Zheng, Yanjie Le, Lu Sun, and Tianyu Ruan. "Improving The Delivery Capacity Of Submarine Cable Landing Section By Air And Water Forced Circulation Cooling System." In 2024 China International Conference on Electricity Distribution (CICED). IEEE, 2024. http://dx.doi.org/10.1109/ciced63421.2024.10753878.

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Zurecki, Z., R. Ghosh, T. Mebrahtu, M. J. Thayer, and S. R. Stringer. "Automated Substrate Cooling System for HVOF Coating Operations." In ITSC2008, edited by B. R. Marple, M. M. Hyland, Y. C. Lau, C. J. Li, R. S. Lima, and G. Montavon. Verlag für Schweißen und verwandte Verfahren DVS-Verlag GmbH, 2008. http://dx.doi.org/10.31399/asm.cp.itsc2008p0206.

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Abstract High production rate and feed powder efficiency are critical in the HVOF hardfacing of aircraft landing gear, turbine, and actuator components traditionally electroplated with carcinogenic hard chromium. Desired improvements are hindered by rapid heat build-up in substrate component and thermal expansion mismatch between the carbide coating and steel, titanium or aluminum substrate. A new, cryogenic nitrogen gas (-195°C) cooling system has been developed which limits the thermal expansion and substrate softening problems, and enables a non-stop, gun-on-target spraying. Fully automated
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Akuh, M., L. Mercando, and Z. Zurecki. "Cryo-Gas Cooling Method and System for Thermal Spray Coatings." In ITSC2011, edited by B. R. Marple, A. Agarwal, M. M. Hyland, et al. DVS Media GmbH, 2011. http://dx.doi.org/10.31399/asm.cp.itsc2011p1411.

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Abstract Thermal spray coating applications require precise control of substrate temperature during deposition in order to achieve optimum performance of the final part. Applications such as high-velocity oxy-fuel (HVOF) hardfacing of aircraft landing gear and plasma spraying of thick sputtering targets are but a few examples where control of substrate temperature throughout the entire coating cycle is critical. A broad effort to develop a versatile and cost-effective cryogenic gas cooling system for controlling part temperature in high-energy thermal spray operations is described. Results sho
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Cederbond, Walid, and Atilla Dogan. "Gear-Up Landing Prevention System." In AIAA Guidance, Navigation, and Control Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-6439.

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Méry, Dominique, and Neeraj Kumar Singh. "Formal evaluation of landing gear system." In the Fifth Symposium. ACM Press, 2014. http://dx.doi.org/10.1145/2676585.2676599.

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Tartaruga, Irene, Mark H. Lowenberg, Jonathan E. Cooper, Pia Sartor, and Yves Lemmens. "Bifurcation Analysis of a Nose Landing Gear System." In 15th Dynamics Specialists Conference. American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-1572.

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